WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 200,000 Max Cl/Cd: 76.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601261-il-200000-n5.txt Download as CSV file: xf-fx601261-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2606 0.08831 0.08505 -0.0449 1.0000 0.0138
-9.750 -0.2658 0.08444 0.08124 -0.0450 1.0000 0.0136
-9.250 -0.4084 0.06809 0.06450 -0.0569 1.0000 0.0114
-9.000 -0.4257 0.06354 0.05998 -0.0582 1.0000 0.0113
-8.750 -0.4275 0.05846 0.05489 -0.0636 0.9950 0.0112
-8.500 -0.4265 0.05036 0.04658 -0.0768 0.9754 0.0111
-8.250 -0.4092 0.04377 0.03971 -0.0898 0.9595 0.0110
-8.000 -0.3900 0.03849 0.03400 -0.0980 0.9468 0.0108
-7.750 -0.3643 0.03408 0.02911 -0.1040 0.9373 0.0107
-7.500 -0.3314 0.03047 0.02501 -0.1091 0.9313 0.0106
-7.250 -0.3003 0.02779 0.02190 -0.1122 0.9232 0.0107
-7.000 -0.2644 0.02575 0.01932 -0.1154 0.9171 0.0112
-6.750 -0.2321 0.02379 0.01711 -0.1176 0.9103 0.0117
-6.500 -0.1989 0.02225 0.01545 -0.1195 0.9038 0.0121
-6.250 -0.1652 0.02087 0.01384 -0.1210 0.8972 0.0120
-6.000 -0.1336 0.01974 0.01254 -0.1220 0.8888 0.0119
-5.750 -0.1024 0.01875 0.01143 -0.1229 0.8806 0.0118
-5.500 -0.0725 0.01787 0.01046 -0.1236 0.8718 0.0118
-5.250 -0.0436 0.01708 0.00961 -0.1240 0.8634 0.0118
-5.000 -0.0144 0.01637 0.00884 -0.1246 0.8558 0.0118
-4.750 0.0144 0.01571 0.00811 -0.1251 0.8484 0.0119
-4.500 0.0434 0.01515 0.00744 -0.1256 0.8407 0.0120
-4.250 0.0725 0.01466 0.00684 -0.1260 0.8332 0.0121
-4.000 0.1014 0.01424 0.00630 -0.1263 0.8250 0.0123
-3.750 0.1303 0.01389 0.00583 -0.1265 0.8167 0.0125
-3.500 0.1591 0.01359 0.00540 -0.1266 0.8080 0.0129
-3.250 0.1876 0.01334 0.00504 -0.1267 0.7995 0.0133
-3.000 0.2165 0.01314 0.00472 -0.1268 0.7920 0.0140
-2.750 0.2451 0.01293 0.00443 -0.1268 0.7841 0.0151
-2.500 0.2739 0.01275 0.00415 -0.1268 0.7761 0.0181
-2.250 0.3036 0.01169 0.00375 -0.1281 0.7674 0.1965
-2.000 0.3327 0.01117 0.00369 -0.1287 0.7589 0.3317
-1.750 0.3604 0.01108 0.00378 -0.1286 0.7488 0.3998
-1.500 0.3886 0.01109 0.00376 -0.1285 0.7396 0.4241
-1.250 0.4165 0.01111 0.00378 -0.1283 0.7304 0.4480
-1.000 0.4443 0.01116 0.00383 -0.1281 0.7214 0.4718
-0.750 0.4723 0.01121 0.00382 -0.1278 0.7119 0.4869
-0.500 0.4998 0.01122 0.00380 -0.1276 0.7008 0.4954
-0.250 0.5275 0.01125 0.00377 -0.1274 0.6901 0.5043
0.000 0.5552 0.01128 0.00376 -0.1271 0.6799 0.5120
0.250 0.5828 0.01133 0.00376 -0.1269 0.6690 0.5206
0.500 0.6103 0.01137 0.00380 -0.1267 0.6587 0.5285
0.750 0.6379 0.01145 0.00381 -0.1264 0.6487 0.5380
1.000 0.6650 0.01150 0.00387 -0.1261 0.6367 0.5464
1.250 0.6921 0.01158 0.00392 -0.1258 0.6238 0.5561
1.500 0.7189 0.01167 0.00398 -0.1255 0.6106 0.5654
1.750 0.7457 0.01176 0.00405 -0.1251 0.5980 0.5740
2.000 0.7725 0.01187 0.00414 -0.1248 0.5861 0.5831
2.250 0.7991 0.01197 0.00426 -0.1244 0.5734 0.5919
2.500 0.8256 0.01209 0.00437 -0.1240 0.5608 0.6022
2.750 0.8517 0.01222 0.00450 -0.1236 0.5473 0.6131
3.000 0.8773 0.01236 0.00463 -0.1231 0.5314 0.6248
3.250 0.9024 0.01253 0.00479 -0.1224 0.5123 0.6380
3.500 0.9270 0.01272 0.00494 -0.1217 0.4923 0.6523
3.750 0.9516 0.01291 0.00512 -0.1210 0.4728 0.6676
4.000 0.9758 0.01312 0.00534 -0.1203 0.4523 0.6842
4.250 0.9991 0.01335 0.00556 -0.1194 0.4297 0.7042
4.500 1.0219 0.01361 0.00579 -0.1184 0.4065 0.7289
4.750 1.0436 0.01388 0.00606 -0.1172 0.3819 0.7607
5.000 1.0632 0.01411 0.00633 -0.1155 0.3580 0.8081
5.250 1.0791 0.01417 0.00649 -0.1129 0.3401 1.0000
5.500 1.1033 0.01455 0.00682 -0.1124 0.3217 1.0000
5.750 1.1265 0.01499 0.00717 -0.1117 0.3011 1.0000
6.000 1.1493 0.01545 0.00757 -0.1110 0.2832 1.0000
6.250 1.1719 0.01592 0.00798 -0.1102 0.2647 1.0000
6.500 1.1937 0.01644 0.00843 -0.1094 0.2448 1.0000
6.750 1.2148 0.01699 0.00891 -0.1084 0.2272 1.0000
7.000 1.2359 0.01754 0.00943 -0.1075 0.2101 1.0000
7.250 1.2560 0.01814 0.00997 -0.1064 0.1920 1.0000
7.500 1.2752 0.01878 0.01056 -0.1052 0.1781 1.0000
7.750 1.2941 0.01942 0.01118 -0.1040 0.1636 1.0000
8.250 1.3259 0.02103 0.01261 -0.1007 0.1304 1.0000
8.500 1.3402 0.02182 0.01335 -0.0989 0.1165 1.0000
8.750 1.3545 0.02255 0.01407 -0.0970 0.1031 1.0000
9.000 1.3678 0.02334 0.01485 -0.0950 0.0958 1.0000
9.250 1.3807 0.02416 0.01568 -0.0931 0.0908 1.0000
9.500 1.3952 0.02488 0.01649 -0.0914 0.0862 1.0000
9.750 1.4077 0.02575 0.01742 -0.0895 0.0813 1.0000
10.000 1.4200 0.02665 0.01838 -0.0877 0.0768 1.0000
10.500 1.4407 0.02881 0.02059 -0.0842 0.0628 1.0000
10.750 1.4482 0.03016 0.02193 -0.0824 0.0583 1.0000
11.000 1.4580 0.03140 0.02325 -0.0808 0.0544 1.0000
11.250 1.4663 0.03279 0.02472 -0.0794 0.0505 1.0000
11.500 1.4738 0.03431 0.02631 -0.0779 0.0465 1.0000
11.750 1.4840 0.03564 0.02776 -0.0768 0.0417 1.0000
12.000 1.4903 0.03737 0.02954 -0.0756 0.0374 1.0000
12.250 1.4959 0.03922 0.03145 -0.0745 0.0356 1.0000
12.500 1.5005 0.04124 0.03352 -0.0735 0.0337 1.0000
12.750 1.5041 0.04342 0.03576 -0.0726 0.0318 1.0000
13.000 1.5079 0.04566 0.03812 -0.0718 0.0301 1.0000
13.250 1.5110 0.04804 0.04062 -0.0712 0.0288 1.0000
13.500 1.5131 0.05062 0.04331 -0.0708 0.0276 1.0000
13.750 1.5139 0.05343 0.04623 -0.0705 0.0266 1.0000
14.000 1.5136 0.05646 0.04939 -0.0704 0.0257 1.0000
14.250 1.5146 0.05944 0.05250 -0.0704 0.0250 1.0000
14.500 1.5177 0.06224 0.05547 -0.0705 0.0242 1.0000
14.750 1.5200 0.06524 0.05863 -0.0708 0.0234 1.0000
15.000 1.5213 0.06845 0.06201 -0.0713 0.0223 1.0000
15.250 1.5219 0.07184 0.06560 -0.0719 0.0206 1.0000
15.500 1.5210 0.07555 0.06946 -0.0727 0.0167 1.0000
15.750 1.5067 0.08142 0.07529 -0.0745 0.0097 1.0000
16.000 1.4930 0.08746 0.08140 -0.0766 0.0058 1.0000
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